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Drive system for landing gear

a technology of driving system and landing gear, which is applied in the direction of landing gear, wheel arrangement, aircraft components, etc., can solve the problems of high brake wear, high fuel consumption, and increased local level of both atmospheric and noise pollution around airports

Active Publication Date: 2016-08-04
AIRBUS OPERATIONS LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text describes a lock-stay mechanism for an aircraft that can be moved between two positions to engage or disengage the drive pinion and driven gear. The mechanism includes a linear actuator that is connected to the lock links and a common pivot joint. The actuator is positioned at the pivotal connection between the lock links, which provides mechanical advantage and simplifies the coupling. The lock-stay can move in a vertical plane between the two positions, with the second position being below the first position to aid in the movement caused by gravity. The technical effect of this mechanism is to reduce part count, weight, and cost savings while also simplifying the engagement and disengagement process of the lock-stay mechanism.

Problems solved by technology

This means that there is a relatively high fuel consumption as a result of the poor propulsion efficiency at this low power.
This leads to an increased level of both atmospheric and noise pollution locally around airports.
Moreover, even when the engines are run at low power it is generally necessary to apply the wheel brakes to limit ground taxi speeds, leading to a high degree of brake wear.
This process is laborious and costly.

Method used

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  • Drive system for landing gear
  • Drive system for landing gear
  • Drive system for landing gear

Examples

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first embodiment

[0047]the invention is shown in FIGS. 1 to 5. In the illustrated embodiment the landing gear has two wheels, but the principles of the embodiment may be applied to landing gear with four or more wheels. The embodiment shows a main landing gear (i.e. a landing gear attached to wing structure or fuselage structure in the region of the wings), since the weight supported by the main landing gear is considered to provide the best traction between the wheels and the ground to enable reliable aircraft ground taxiing. However, the drive system of the present invention may alternatively be applied to a nose landing gear (i.e. a steerable landing gear towards the nose of the aircraft). The main landing gear shown is applicable to a single aisle passenger airliner (approximately 150-200 pax), although it will be appreciated that this invention has wide applicability to a variety of aircraft types and weights, including civil aircraft, military aircraft, helicopters, passenger aircraft (450 pax...

second embodiment

[0082]Whilst in the second embodiment described above the drive path between the input shaft and the output shaft of the gearbox comprises a two stage parallel axis gear arrangement it will be appreciated that other torque transmission arrangements may be used instead. For example, the number of stages may be any number including only a single stage, and the torque transmission may be via a belt / cable or chain instead of gears. It will also be appreciated that the stage(s) of the drive path need not be mounted on parallel axes and skew axis torque transmission arrangements may be used instead.

[0083]Also, whilst in the illustrated second embodiment the motor is fixed to the bracket, the motor can alternatively be mounted to rotate relative to the bracket so as to rotate with the gearbox 70a about the pivotal connection between the housing 84a and the bracket 56a. In this case the loads on the actuator (positioner) will still be reduced as compared with the drive system of the first e...

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PUM

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Abstract

The invention relates to a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system further includes a lock-stay including a first lock link and a second lock link pivotally connected to the first lock link, the lock-stay being switchable between a first position, a second position, and an intermediate position between the first and second positions in which the first and second lock links are substantially aligned. The lock-stay is in the first position when the drive system is in the first configuration and the lock-stay is in the second position when the drive system is in the second configuration. Also, an aircraft landing gear including a wheel and the drive system according in which the driven gear is mounted to the wheel.

Description

BACKGROUND OF THE INVENTION[0001]The present invention relates to a drive system for rotating one or more wheels of an aircraft landing gear for the purposes of ground taxiing (forwards or reverse) and / or wheel spin-up prior to landing and / or for applying braking torque to the rotating wheel(s).BACKGROUND OF THE INVENTION[0002]Aircraft are required to ground taxi between locations on airfields. An example is taxiing between a runway and the location (e.g. terminal gate) at which the aircraft's passengers are to board or disembark. Typically, such taxiing is achieved by using the thrust from the aircraft's engines to propel the aircraft forwards so that the landing gear wheels are caused to rotate. Since ground taxi speeds are necessarily relatively low, the engines must be run at a very low power. This means that there is a relatively high fuel consumption as a result of the poor propulsion efficiency at this low power.[0003]This leads to an increased level of both atmospheric and n...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): B64C25/40B64C25/34
CPCB64C25/405Y02T50/823B64C25/34Y02T50/80
Inventor DIDEY, ARNAUD
Owner AIRBUS OPERATIONS LTD
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